GOE 155 (SSW D.1) AIRFOIL (goe155-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 155 (SSW D.1) AIRFOIL (goe155-il) Reynolds number: 1,000,000 Max Cl/Cd: 123.25 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe155-il-1000000.txt Download as CSV file: xf-goe155-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 155 (SSW D.1) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3589 0.10323 0.10170 -0.0136 0.9557 0.0109
-8.500 -0.3581 0.09932 0.09776 -0.0138 0.9425 0.0110
-8.250 -0.3523 0.09646 0.09488 -0.0139 0.9314 0.0111
-8.000 -0.3460 0.09384 0.09224 -0.0145 0.9202 0.0113
-7.750 -0.3393 0.09121 0.08958 -0.0156 0.9083 0.0114
-7.500 -0.3324 0.08855 0.08687 -0.0169 0.8957 0.0117
-7.250 -0.3231 0.08569 0.08397 -0.0192 0.8833 0.0121
-7.000 -0.3101 0.08241 0.08065 -0.0226 0.8709 0.0129
-6.750 -0.2877 0.07748 0.07565 -0.0314 0.8581 0.0141
-6.500 -0.2667 0.07297 0.07108 -0.0379 0.8470 0.0142
-6.250 -0.2454 0.06869 0.06672 -0.0429 0.8371 0.0142
-6.000 -0.1912 0.04893 0.04695 -0.0436 0.8002 0.0147
-5.750 -0.1746 0.04612 0.04409 -0.0457 0.7927 0.0151
-5.500 -0.1555 0.04271 0.04062 -0.0490 0.7850 0.0157
-5.250 -0.1337 0.03885 0.03670 -0.0531 0.7783 0.0167
-5.000 -0.0967 0.03282 0.03052 -0.0621 0.7732 0.0182
-4.750 -0.0703 0.02830 0.02587 -0.0662 0.7679 0.0182
-3.750 0.0238 0.03239 0.02935 -0.0787 0.7610 0.0209
-3.500 0.0618 0.02898 0.02567 -0.0804 0.7553 0.0233
-3.250 0.0944 0.02084 0.01690 -0.0830 0.7507 0.0240
-3.000 0.1213 0.01954 0.01553 -0.0836 0.7446 0.0246
-2.750 0.1487 0.01861 0.01448 -0.0840 0.7380 0.0252
-2.500 0.1770 0.01748 0.01321 -0.0844 0.7314 0.0262
-2.250 0.2061 0.01628 0.01179 -0.0846 0.7245 0.0284
-2.000 0.2359 0.01645 0.01178 -0.0844 0.7184 0.0301
-1.750 0.2649 0.01291 0.00780 -0.0851 0.7125 0.0320
-1.500 0.2931 0.01232 0.00713 -0.0853 0.7061 0.0330
-1.250 0.3218 0.01177 0.00650 -0.0855 0.6990 0.0345
-1.000 0.3504 0.01130 0.00590 -0.0856 0.6917 0.0364
-0.750 0.3792 0.01193 0.00649 -0.0855 0.6825 0.0389
-0.500 0.4076 0.01026 0.00466 -0.0860 0.6744 0.0437
-0.250 0.4375 0.00893 0.00307 -0.0856 0.6661 0.0319
0.000 0.4662 0.00857 0.00266 -0.0857 0.6577 0.0317
0.500 0.5232 0.00806 0.00207 -0.0858 0.6374 0.0320
0.750 0.5518 0.00791 0.00188 -0.0860 0.6252 0.0320
1.000 0.5802 0.00780 0.00172 -0.0861 0.6105 0.0320
1.250 0.6086 0.00773 0.00158 -0.0862 0.5926 0.0328
1.500 0.6369 0.00772 0.00150 -0.0863 0.5713 0.0329
1.750 0.6650 0.00777 0.00145 -0.0864 0.5457 0.0332
2.000 0.6929 0.00788 0.00143 -0.0865 0.5173 0.0339
2.250 0.7208 0.00800 0.00144 -0.0866 0.4902 0.0358
2.500 0.7487 0.00813 0.00148 -0.0867 0.4678 0.0378
2.750 0.7765 0.00826 0.00154 -0.0868 0.4499 0.0405
3.000 0.8044 0.00836 0.00165 -0.0869 0.4347 0.0701
3.250 0.8321 0.00840 0.00181 -0.0870 0.4184 0.1600
3.500 0.8557 0.00699 0.00209 -0.0867 0.4014 1.0000
3.750 0.8833 0.00717 0.00221 -0.0867 0.3874 1.0000
4.000 0.9106 0.00739 0.00233 -0.0868 0.3697 1.0000
4.250 0.9379 0.00761 0.00248 -0.0868 0.3478 1.0000
4.500 0.9647 0.00790 0.00264 -0.0868 0.3217 1.0000
4.750 0.9911 0.00826 0.00284 -0.0868 0.2910 1.0000
5.000 1.0172 0.00864 0.00309 -0.0867 0.2636 1.0000
5.250 1.0434 0.00899 0.00333 -0.0867 0.2429 1.0000
5.750 1.0957 0.00963 0.00381 -0.0865 0.2106 1.0000
6.000 1.1215 0.00998 0.00408 -0.0864 0.1892 1.0000
6.500 1.1608 0.01253 0.00576 -0.0847 0.0304 1.0000
6.750 1.1851 0.01304 0.00627 -0.0843 0.0244 1.0000
7.000 1.2102 0.01339 0.00665 -0.0840 0.0222 1.0000
7.250 1.2341 0.01391 0.00719 -0.0836 0.0191 1.0000
7.500 1.2577 0.01443 0.00776 -0.0831 0.0172 1.0000
7.750 1.2819 0.01482 0.00817 -0.0827 0.0159 1.0000
8.000 1.3055 0.01527 0.00865 -0.0822 0.0147 1.0000
8.250 1.3263 0.01606 0.00950 -0.0813 0.0132 1.0000
8.500 1.3466 0.01684 0.01037 -0.0804 0.0125 1.0000
8.750 1.3687 0.01735 0.01093 -0.0797 0.0119 1.0000
9.000 1.3903 0.01789 0.01150 -0.0790 0.0112 1.0000
9.250 1.4112 0.01844 0.01208 -0.0782 0.0105 1.0000
9.500 1.4303 0.01914 0.01283 -0.0772 0.0100 1.0000
9.750 1.4414 0.02050 0.01429 -0.0750 0.0093 1.0000
10.000 1.4499 0.02192 0.01584 -0.0725 0.0089 1.0000
10.250 1.4645 0.02267 0.01666 -0.0708 0.0087 1.0000
10.500 1.4740 0.02359 0.01765 -0.0684 0.0085 1.0000
10.750 1.4815 0.02473 0.01888 -0.0660 0.0083 1.0000
11.000 1.4888 0.02598 0.02023 -0.0638 0.0080 1.0000
11.250 1.4957 0.02735 0.02169 -0.0618 0.0078 1.0000
11.500 1.5025 0.02881 0.02323 -0.0601 0.0076 1.0000
11.750 1.5101 0.03027 0.02476 -0.0586 0.0073 1.0000
12.000 1.5188 0.03169 0.02624 -0.0574 0.0071 1.0000
12.250 1.5253 0.03335 0.02797 -0.0562 0.0069 1.0000
12.500 1.5268 0.03558 0.03027 -0.0548 0.0066 1.0000
12.750 1.5183 0.03891 0.03374 -0.0529 0.0064 1.0000
13.000 1.5052 0.04288 0.03789 -0.0508 0.0062 1.0000
13.250 1.5087 0.04516 0.04028 -0.0501 0.0062 1.0000
13.500 1.5113 0.04761 0.04284 -0.0495 0.0061 1.0000
13.750 1.5118 0.05033 0.04568 -0.0489 0.0060 1.0000
14.000 1.5103 0.05335 0.04882 -0.0485 0.0059 1.0000
14.250 1.5074 0.05661 0.05221 -0.0481 0.0058 1.0000
14.500 1.5033 0.06008 0.05582 -0.0479 0.0057 1.0000
14.750 1.4981 0.06388 0.05975 -0.0479 0.0056 1.0000
15.000 1.4916 0.06797 0.06398 -0.0481 0.0055 1.0000
15.250 1.4845 0.07229 0.06844 -0.0487 0.0055 1.0000
15.500 1.4760 0.07699 0.07329 -0.0496 0.0054 1.0000
15.750 1.4666 0.08201 0.07846 -0.0507 0.0054 1.0000
16.000 1.4559 0.08736 0.08397 -0.0522 0.0053 1.0000
16.250 1.4435 0.09317 0.08993 -0.0541 0.0053 1.0000
16.500 1.4310 0.09922 0.09614 -0.0563 0.0052 1.0000
16.750 1.4165 0.10576 0.10283 -0.0589 0.0052 1.0000
17.000 1.4016 0.11257 0.10980 -0.0618 0.0052 1.0000
17.250 1.3847 0.12002 0.11741 -0.0652 0.0052 1.0000
17.500 1.3646 0.12837 0.12593 -0.0694 0.0052 1.0000
17.750 1.3433 0.13731 0.13505 -0.0741 0.0052 1.0000
18.000 1.3221 0.14674 0.14464 -0.0794 0.0052 1.0000
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